ISO 16454:2024 航天系统 结构设计 应力分析要求

标准编号：ISO 16454:2024

中文名称：航天系统 结构设计 应力分析要求

英文名称：Space systems — Structural design — Stress analysis requirements

发布日期：2024-03

标准范围

本文件提供了确定载荷下最大应力和相应安全裕度的要求，并定义了静态强度失效模式的标准，如破裂、倒塌和有害屈服。本文件不包括临界条件引起的疲劳、蠕变和裂纹扩展。尽管存在这些范围限制，但基于本文件要求的应力计算结果适用于其他临界条件分析。本文件适用于运载火箭和航天器承载元件设计中应力/应变分布和安全裕度的确定。液体推进剂发动机结构、固体推进剂发动机喷管和固体推进剂本身不包括在内，但液体推进剂贮箱、压力容器和固体推进剂壳体在本文件的范围内。根据本文件的要求，应力计算的模型、方法和程序也可以适用于所考虑的子结构和结构元件的位移和变形计算以及载荷计算。当应用本文档时，假设温度分布已经被确定并用作输入数据。

This document provides requirements for the determination of maximum stress and corresponding margin of safety under loading and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. This document does not cover critical-conditions-induced fatigue, creep and crack growths. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of this document are applicable to other critical condition analysis.

This document is applicable to the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft load-bearing elements design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of this document.

In accordance with the requirements of this document, the models, methods and procedures for stress calculation can also be applicable to the displacements and deformation calculation, as well as the calculation of loads, applied to substructures and structural elements under consideration. When this document is applied, it is assumed that temperature distribution has been determined and is used as input data.

标准预览图